A gas turbine engine blade containment assembly

(19)

(11)

EP 1 087 104 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	12.11.2003 Bulletin 2003/46

(43)	Date of publication A2:
	28.03.2001 Bulletin 2001/13

(21)	Application number: 00307954.8

(22)	Date of filing: 13.09.2000

(51)	International Patent Classification (IPC)⁷: F01D 21/04

(84)	Designated Contracting States:
	AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE
	Designated Extension States:
	AL LT LV MK RO SI

(30)

Priority:

25.09.1999 GB 9922619

(71)	Applicant: ROLLS-ROYCE PLC
	London, SW1E 6AT (GB)

(72)	Inventors:
	Sathianathan, Sivasubramaniam Kathirgamathamby Stretton, Burton on Trent DE13 OFX (GB) Martindale, Ian Graham Ashbourne Derby DE6 5JA (GB) Geary, David Mickleover, Derby DE3 5TB (GB) Reed, Julian Mark Littleover, Derby DE23 7WS (GB)

(74)	Representative: Gunn, Michael Alan
	Rolls-Royce plc P.O. Box 31 Derby DE24 8BJ Derby DE24 8BJ (GB)

(54)	A gas turbine engine blade containment assembly

(57) A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular hook (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular hook (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). The metal casing (40) has a containment portion (A) downstream of the annular hook (54) and substantially in the plane of the leading edge of the tip (37) of the fan blade (34). The containment portion (A) of the casing (40) has a greater diameter than the diameter of the casing (40) at the annular hook (54) to restrain upstream movement of a detached fan blade (34).

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